Search
Now showing items 1-3 of 3
Film-Cooling on a Gas Turbine Blade Pressure Side or Suction Side With Compound Angle Shaped Holes
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The film-cooling effectiveness on the surface of a high pressure turbine blade is measured using the pressure sensitive paint technique. Compound angle laidback fan-shaped holes are used to cool ...
Influence of Coolant Density on Turbine Blade Platform Film-Cooling
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Detailed parametric study of film-cooling effectiveness was carried out on a turbine blade platform of a five-blade linear cascade. The parameters chosen were freestream turbulence intensity, ...
Influence of Coolant Density on Turbine Blade Film-Cooling Using Pressure Sensitive Paint Technique
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Adiabatic film-cooling effectiveness is examined on a high-pressure turbine blade by varying three critical engine parameters, viz., coolant blowing ratio, coolant-to-mainstream density ratio, and ...